Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3 Turbofan Engines, 8263-8265 [E7-3017]
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Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Rules and Regulations
adverse effects of HIRF. Therefore, we
consider this system to be a novel or
unusual design feature.
Frequency
Peak
ycherry on PROD1PC64 with RULES
Discussion
There is no specific regulation that
addresses protection requirements for
electrical and electronic systems from
HIRF. Increased power levels from
ground-based radio transmitters and the
growing use of sensitive avionics/
electronics and electrical systems to
command and control airplanes have
made it necessary to provide adequate
protection.
To ensure that a level of safety is
achieved equivalent to that intended by
the regulations incorporated by
reference, special conditions are needed
for the Raytheon Aircraft Company
Model BAe.125 Series 800A airplanes
modified by Duncan Aviation, Inc.
These special conditions require that
new avionics/electronics and electrical
systems that perform critical functions
be designed and installed to preclude
component damage and interruption of
function because of both the direct and
indirect effects of HIRF.
High-Intensity Radiated Fields (HIRF)
With the trend toward increased
power levels from ground-based
transmitters, and the advent of space
and satellite communications, coupled
with electronic command and control of
the airplane, the immunity of critical
avionics/electronics and electrical
systems to HIRF must be established.
It is not possible to precisely define
the HIRF to which the airplane will be
exposed in service. There is also
uncertainty concerning the effectiveness
of airframe shielding for HIRF.
Furthermore, coupling of
electromagnetic energy to cockpitinstalled equipment through the cockpit
window apertures is undefined. Based
on surveys and analysis of existing HIRF
emitters, an adequate level of protection
exists when compliance with the HIRF
protection special condition is shown
with either paragraph 1 OR 2 below:
1. A minimum threat of 100 volts rms
(root-mean-square) per meter electric
field strength from 10 KHz to 18 GHz.
a. The threat must be applied to the
system elements and their associated
wiring harnesses without the benefit of
airframe shielding.
b. Demonstration of this level of
protection is established through system
tests and analysis.
2. A threat external to the airframe of
the field strengths identified in the table
below for the frequency ranges
indicated. Both peak and average field
strength components from the table are
to be demonstrated.
VerDate Aug<31>2005
15:57 Feb 23, 2007
Jkt 211001
Field Strength
(volts per meter)
10 kHz–100 kHz ...........
100 kHz–500 kHz .........
500 kHz–2 MHz ............
2 MHz–30 MHz .............
30 MHz–70 MHz ...........
70 MHz–100 MHz .........
100 MHz–200 MHz .......
200 MHz–400 MHz .......
400 MHz–700 MHz .......
700 MHz–1 GHz ...........
1 GHz–2 GHz ...............
2 GHz–4 GHz ...............
4 GHz–6 GHz ...............
6 GHz–8 GHz ...............
8 GHz–12 GHz .............
12 GHz–18 GHz ...........
18 GHz–40 GHz ...........
50
50
50
100
50
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
Average
50
50
50
100
50
50
100
100
50
100
200
200
200
200
300
200
200
The field strengths are expressed in terms
of peak of the root-mean-square (rms) over
the complete modulation period.
The threat levels identified above are
the result of an FAA review of existing
studies on the subject of HIRF, in light
of the ongoing work of the
Electromagnetic Effects Harmonization
Working Group of the Aviation
Rulemaking Advisory Committee.
Applicability
As discussed above, these special
conditions are applicable to Raytheon
Aircraft Company Model BAe.125 Series
800A airplanes modified by Duncan
Aviation, Inc. Should Duncan Aviation,
Inc. apply later for a supplemental type
certificate to modify any other model
included on Type Certificate No. A3EU
to incorporate the same or similar novel
or unusual design feature, these special
conditions would apply to that model as
well.
Conclusion
This action affects only certain novel
or unusual design features on Raytheon
Aircraft Company Model BAe.125 Series
800A airplanes as modified by Duncan
Aviation, Inc. It is not a rule of general
applicability and affects only the
applicant who applied to the FAA for
approval of these features on the
airplane.
The substance of these special
conditions has been subjected to the
notice and comment procedure in
several prior instances and has been
derived without substantive change
from those previously issued. Because a
delay would significantly affect the
certification of the airplane, which is
imminent, the FAA has determined that
prior public notice and comment are
unnecessary and impracticable, and
good cause exists for adopting these
special conditions upon issuance. The
FAA is requesting comments to allow
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
8263
interested persons to send views that
may not have been sent in response to
the prior opportunities for comment
described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
I The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the supplemental type
certification basis for Raytheon Aircraft
Company Model BAe.125 Series 800A
airplanes modified by Duncan Aviation,
Inc.
1. Protection from Unwanted Effects
of High-Intensity Radiated Fields
(HIRF). Each electrical and electronic
system that performs critical functions
must be designed and installed to
ensure that the operation and
operational capability of these systems
to perform critical functions are not
adversely affected when the airplane is
exposed to high-intensity radiated
fields.
2. For the purpose of these special
conditions, the following definition
applies: Critical Functions: Functions
whose failure would contribute to or
cause a failure condition that would
prevent the continued safe flight and
landing of the airplane.
I
Issued in Renton, Washington, on February
12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–3231 Filed 2–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24034; Directorate
Identifier 2006–NE–05–AD; Amendment 39–
14959; AD 2007–04–26]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney PW4077D, PW4084D, PW4090,
and PW4090–3 Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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8264
Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Rules and Regulations
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
Pratt & Whitney PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engines that were reassembled with
previously used high pressure
compressor (HPC) exit brush seal packs
and new or refurbished HPC exit
diffuser air seal lands. That AD
currently requires replacing the HPC
exit inner and outer brush seal packs
with new brush seal packs, or replacing
the HPC exit brush seal assembly with
a new HPC exit brush seal assembly.
This AD requires replacing the HPC exit
inner and outer brush seal packs with
new brush seal packs, using either
original equipment manufactured
(OEM) parts, or FAA-approved part
manufacturer approval (PMA) parts.
This proposed AD also applies to
engines reassembled with a PMA HPC
exit inner and or outer brush seal packs.
This AD results from a request to
include PMA HPC exit inner and outer
brush seal packs and to include the
engines with PMA parts already
installed, in the AD. We are issuing this
AD to prevent uncontained engine
failure, damage to the airplane, and
injury to passengers.
This AD becomes effective April
2, 2007.
DATES:
You may examine the AD
docket on the Internet at https://
dms.dot.gov or in Room PL–401 on the
plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Antonio Cancelliere, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5213; telephone
(781) 238–7751; fax (781) 238–7199; email: antonio.cancelliere@faa.gov.
The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to Pratt & Whitney PW4077D,
PW4084D, PW4090, and PW4090–3
turbofan engines that were reassembled
with previously used HPC exit brush
seal packs and new or refurbished HPC
exit diffuser air seal lands. We
published the proposed AD in the
Federal Register on November 20, 2006
(71 FR 67073). That action proposed to
require replacing the HPC exit inner and
outer brush seal packs with new brush
seal packs, using either OEM parts, or
FAA-approved PMA parts. That action
also proposed to apply to engines
reassembled with a PMA HPC exit inner
and or outer brush seal packs.
ycherry on PROD1PC64 with RULES
SUPPLEMENTARY INFORMATION:
VerDate Aug<31>2005
15:57 Feb 23, 2007
Jkt 211001
Examining the AD Docket
Conclusion
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Add Part Numbers in the
AD Applicability
One commenter, All Nippon Airways,
requests that we add Pratt & Whitney
and PMA part numbers in the AD
applicability to avoid confusion as to
what parts are to be removed and
replaced.
We do not agree. We adequately
identified the parts requiring
replacement, as well as the unsafe
condition, in the proposed AD. Pratt &
Whitney part numbers can be found in
Alert Service Bulletin No. PW4G–112–
A72–280, Revision 2, dated January 12,
2007, which we refer to as additional
information. We did not change the AD.
Request To Allow Installing an HPC
Exit Brush Seal Assembly
One commenter, Pratt & Whitney,
requests that we also allow installing an
HPC exit brush seal assembly, in lieu of
installing an HPC exit brush seal pack,
to comply with the AD.
We agree. Compliance with the AD
can be achieved by installing either an
HPC exit brush seal pack or an HPC exit
brush seal assembly. Although installing
an HPC exit brush seal assembly may be
more costly for operators, it may be
more convenient. We changed the AD
compliance to allow for either
replacement.
Used Part Prohibition
For clarification, we added a used
part prohibition paragraph in the
compliance section. It states that engine
reassembly with used OEM or used
FAA-approved PMA HPC exit inner and
outer brush seal packs with OEM or
FAA-approved PMA new HPC exit
inner and outer brush seal lands, is
prohibited.
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Fmt 4700
Sfmt 4700
Costs of Compliance
We estimate that this AD will affect
76 Pratt & Whitney PW4077D,
PW4084D, PW4090, and PW4090–3
turbofan engines installed on airplanes
of U.S. registry. We also estimate that it
will take about 9 work-hours per engine
to perform the parts replacement, and
that the average labor rate is $80 per
work-hour. Required parts will cost
about $99,990 per engine. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$7,653,950.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
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26FER1
Federal Register / Vol. 72, No. 37 / Monday, February 26, 2007 / Rules and Regulations
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14729 (71 FR
49335, August 23, 2006), and by adding
a new airworthiness directive,
Amendment 39–14959, to read as
follows:
I
2007–04–26 Pratt & Whitney: Amendment
39–14959. Docket No. FAA–2006–24034;
Directorate Identifier 2006–NE–05–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 2, 2007.
failure, damage to the airplane, and injury to
passengers.
DEPARTMENT OF TRANSPORTATION
Compliance
Federal Aviation Administration
(f) You are responsible for having the
actions required by this AD performed at the
following compliance times, unless the
actions have already been done.
(g) Replace the HPC exit inner and outer
brush seal packs with OEM or FAA-approved
PMA new HPC exit inner and outer brush
seal packs, or an OEM or FAA-approved
PMA new HPC exit brush seal assembly, as
follows:
(1) By 3,000 cycles-in-service (CIS) since a
used HPC exit inner brush seal pack and a
new or refurbished HPC exit diffuser air seal
land were installed in the engine, or by
March 31, 2007, whichever occurs later;
however
(2) If on March 31, 2007, the used HPC exit
inner brush seal pack coupled with a new or
refurbished HPC exit diffuser air seal inner
land assembly has not accumulated 3,000
CIS, then by 3,000 CIS, or December 31,
2008, whichever occurs first.
Used Part Prohibition
(h) Engine reassembly with used OEM or
used FAA-approved PMA HPC exit inner and
outer brush seal packs with OEM or FAAapproved PMA new HPC exit inner and outer
brush seal lands, is prohibited.
(i) Information on replacing HPC exit inner
and outer brush seal packs can be found in
the Pratt & Whitney Alert Service Bulletin
No. PW4G–112–A72–280, Revision 2, dated
January 12, 2007, and in the engine overhaul
manual.
Alternative Methods of Compliance
(j) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Affected ADs
(b) This AD supersedes AD 2006–17–08,
Amendment 39–14729.
ycherry on PROD1PC64 with RULES
Applicability
(c) This AD applies to Pratt & Whitney
PW4077D, PW4084D, PW4090, and PW4090–
3 turbofan engines that were:
(1) Reassembled with a previously used
original equipment manufacturer (OEM) or
part manufacturer approval (PMA) high
pressure compressor (HPC) exit inner brush
seal pack; and
(2) Reassembled with a new or refurbished
OEM or PMA HPC exit diffuser air seal inner
land.
(d) These engines are installed on, but not
limited to, Boeing 777 airplanes.
Related Information
Unsafe Condition
(e) This AD supersedure results from a
request to include PMA HPC exit inner and
outer brush seal packs and to include the
engines with PMA parts already installed, in
the AD. This AD action is the result of a
report of oil leaking into the high pressure
turbine (HPT) interstage cavity and igniting,
leading to an engine case penetration and
engine in-flight shutdown. We are issuing
this AD to prevent uncontained engine
Issued in Burlington, Massachusetts, on
February 16, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–3017 Filed 2–23–07; 8:45 am]
VerDate Aug<31>2005
15:57 Feb 23, 2007
Jkt 211001
8265
(k) Pratt & Whitney Alert Service Bulletin
No. PW4G–112–A72–280, Revision 2, dated
January 12, 2007, also pertains to the subject
of this AD.
(l) Contact Antonio Cancelliere, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803–5213; telephone (781) 238–7751; fax
(781) 238–7199; e-mail:
antonio.cancelliere@faa.gov for more
information about this AD.
BILLING CODE 4910–13–P
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Fmt 4700
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14 CFR Part 71
[Docket No. FAA–2006–26311; Airspace
Docket No. 06–AWP–19]
RIN 2120–AA66
Modification of Class D Airspace; Luke
Air Force Base, AZ
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action modifies Class D
airspace at Luke Air Force Base (LUF),
AZ. This modification is necessary to
contain and protect circling maneuvers
for Category E aircraft executing these
maneuvers in conjunction with
Standard Instrument Approach
Procedures (SIAPs) at the airport.
DATES: Effective Date: 0901 UTC, May
10, 2007. The Director of the Federal
Register approves this incorporation by
reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
FOR FURTHER INFORMATION CONTACT:
Francie Hope, System Support
Specialist, Western Service Center,
AJO2–W2, Federal Aviation
Administration, 15000 Aviation
Boulevard, Lawndale, California 90261,
telephone (310) 725–6502.
SUPPLEMENTARY INFORMATION:
History
On December 7, 2006, the FAA
published in the Federal Register (71
FR 70910) a notice of proposed
rulemaking to revise the Class D
airspace at Luke Air Force Base, AZ.
Interested parties were invited to
participate in this rulemaking effort by
submitting written comments on this
proposal to the FAA. On January 11,
2007, a notice of proposed rulemaking
correction was published in the Federal
Register (72 FR 1301), changing the
legal description to better describe the
requisite airspace. No comments were
received. This modification is the same
as that proposed in the notice. Class D
airspace areas are published in
Paragraph 5000 of FAA Order 7400.9P
dated September 1, 2006, and effective
September 15, 2006, which is
incorporated by reference in 14 CFR
71.1. The Class D airspace designation
listed in this document will be
published subsequently in the Order.
E:\FR\FM\26FER1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 37 (Monday, February 26, 2007)]
[Rules and Regulations]
[Pages 8263-8265]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-3017]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24034; Directorate Identifier 2006-NE-05-AD;
Amendment 39-14959; AD 2007-04-26]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D,
PW4090, and PW4090-3 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 8264]]
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3
turbofan engines that were reassembled with previously used high
pressure compressor (HPC) exit brush seal packs and new or refurbished
HPC exit diffuser air seal lands. That AD currently requires replacing
the HPC exit inner and outer brush seal packs with new brush seal
packs, or replacing the HPC exit brush seal assembly with a new HPC
exit brush seal assembly. This AD requires replacing the HPC exit inner
and outer brush seal packs with new brush seal packs, using either
original equipment manufactured (OEM) parts, or FAA-approved part
manufacturer approval (PMA) parts. This proposed AD also applies to
engines reassembled with a PMA HPC exit inner and or outer brush seal
packs. This AD results from a request to include PMA HPC exit inner and
outer brush seal packs and to include the engines with PMA parts
already installed, in the AD. We are issuing this AD to prevent
uncontained engine failure, damage to the airplane, and injury to
passengers.
DATES: This AD becomes effective April 2, 2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in Room PL-401 on the plaza level of the Nassif
Building, 400 Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5213;
telephone (781) 238-7751; fax (781) 238-7199; e-mail:
antonio.cancelliere@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to Pratt & Whitney PW4077D,
PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled
with previously used HPC exit brush seal packs and new or refurbished
HPC exit diffuser air seal lands. We published the proposed AD in the
Federal Register on November 20, 2006 (71 FR 67073). That action
proposed to require replacing the HPC exit inner and outer brush seal
packs with new brush seal packs, using either OEM parts, or FAA-
approved PMA parts. That action also proposed to apply to engines
reassembled with a PMA HPC exit inner and or outer brush seal packs.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Add Part Numbers in the AD Applicability
One commenter, All Nippon Airways, requests that we add Pratt &
Whitney and PMA part numbers in the AD applicability to avoid confusion
as to what parts are to be removed and replaced.
We do not agree. We adequately identified the parts requiring
replacement, as well as the unsafe condition, in the proposed AD. Pratt
& Whitney part numbers can be found in Alert Service Bulletin No. PW4G-
112-A72-280, Revision 2, dated January 12, 2007, which we refer to as
additional information. We did not change the AD.
Request To Allow Installing an HPC Exit Brush Seal Assembly
One commenter, Pratt & Whitney, requests that we also allow
installing an HPC exit brush seal assembly, in lieu of installing an
HPC exit brush seal pack, to comply with the AD.
We agree. Compliance with the AD can be achieved by installing
either an HPC exit brush seal pack or an HPC exit brush seal assembly.
Although installing an HPC exit brush seal assembly may be more costly
for operators, it may be more convenient. We changed the AD compliance
to allow for either replacement.
Used Part Prohibition
For clarification, we added a used part prohibition paragraph in
the compliance section. It states that engine reassembly with used OEM
or used FAA-approved PMA HPC exit inner and outer brush seal packs with
OEM or FAA-approved PMA new HPC exit inner and outer brush seal lands,
is prohibited.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 76 Pratt & Whitney PW4077D,
PW4084D, PW4090, and PW4090-3 turbofan engines installed on airplanes
of U.S. registry. We also estimate that it will take about 9 work-hours
per engine to perform the parts replacement, and that the average labor
rate is $80 per work-hour. Required parts will cost about $99,990 per
engine. Based on these figures, we estimate the total cost of the AD to
U.S. operators to be $7,653,950.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
[[Page 8265]]
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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2. The FAA amends Sec. 39.13 by removing Amendment 39-14729 (71 FR
49335, August 23, 2006), and by adding a new airworthiness directive,
Amendment 39-14959, to read as follows:
2007-04-26 Pratt & Whitney: Amendment 39-14959. Docket No. FAA-2006-
24034; Directorate Identifier 2006-NE-05-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April 2,
2007.
Affected ADs
(b) This AD supersedes AD 2006-17-08, Amendment 39-14729.
Applicability
(c) This AD applies to Pratt & Whitney PW4077D, PW4084D, PW4090,
and PW4090-3 turbofan engines that were:
(1) Reassembled with a previously used original equipment
manufacturer (OEM) or part manufacturer approval (PMA) high pressure
compressor (HPC) exit inner brush seal pack; and
(2) Reassembled with a new or refurbished OEM or PMA HPC exit
diffuser air seal inner land.
(d) These engines are installed on, but not limited to, Boeing
777 airplanes.
Unsafe Condition
(e) This AD supersedure results from a request to include PMA
HPC exit inner and outer brush seal packs and to include the engines
with PMA parts already installed, in the AD. This AD action is the
result of a report of oil leaking into the high pressure turbine
(HPT) interstage cavity and igniting, leading to an engine case
penetration and engine in-flight shutdown. We are issuing this AD to
prevent uncontained engine failure, damage to the airplane, and
injury to passengers.
Compliance
(f) You are responsible for having the actions required by this
AD performed at the following compliance times, unless the actions
have already been done.
(g) Replace the HPC exit inner and outer brush seal packs with
OEM or FAA-approved PMA new HPC exit inner and outer brush seal
packs, or an OEM or FAA-approved PMA new HPC exit brush seal
assembly, as follows:
(1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner
brush seal pack and a new or refurbished HPC exit diffuser air seal
land were installed in the engine, or by March 31, 2007, whichever
occurs later; however
(2) If on March 31, 2007, the used HPC exit inner brush seal
pack coupled with a new or refurbished HPC exit diffuser air seal
inner land assembly has not accumulated 3,000 CIS, then by 3,000
CIS, or December 31, 2008, whichever occurs first.
Used Part Prohibition
(h) Engine reassembly with used OEM or used FAA-approved PMA HPC
exit inner and outer brush seal packs with OEM or FAA-approved PMA
new HPC exit inner and outer brush seal lands, is prohibited.
(i) Information on replacing HPC exit inner and outer brush seal
packs can be found in the Pratt & Whitney Alert Service Bulletin No.
PW4G-112-A72-280, Revision 2, dated January 12, 2007, and in the
engine overhaul manual.
Alternative Methods of Compliance
(j) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(k) Pratt & Whitney Alert Service Bulletin No. PW4G-112-A72-280,
Revision 2, dated January 12, 2007, also pertains to the subject of
this AD.
(l) Contact Antonio Cancelliere, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5213; telephone (781)
238-7751; fax (781) 238-7199; e-mail: antonio.cancelliere@faa.gov
for more information about this AD.
Issued in Burlington, Massachusetts, on February 16, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-3017 Filed 2-23-07; 8:45 am]
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